The invention is related to an aircraft (1) with a fuselage (2) that defines at least an interior region (2a) and a drive system accommodating region (1f), said drive system accommodating region being arranged inside said fuselage (2) and comprising at least one fire protection zone (11) that is defined by at least one associated firewall arrangement (10), said at least one fire protection zone (11) accommodating at least one engine (5) within said at least one associated firewall arrangement (10) such that said associated firewall arrangement defines a fire-resistant separation between said at least one engine (5) and said interior region (2a) of said fuselage (2), wherein said at least one associated firewall arrangement (10) comprises at least one air duct for ducting a hot air flow that is generated in operation of said aircraft (1) independent from heat generation of said at least one engine (5).
AN AIRCRAFT WITH A FUSELAGE THAT DEFINES AT LEAST AN INTERIOR REGION AND A DRIVE SYSTEM ACCOMMODATING REGION
FLUGZEUG MIT EINEM RUMPF DER MINDESTENS EINEN INNENBEREICH UND EINEN BEREICH ZUR ANTRIEBSUNTERBRINGUNG DEFINIERT
AÉRONEF COMPRENANT UN FUSELAGE QUI DÉFINIT AU MOINS UNE RÉGION INTÉRIEURE ET UNE RÉGION DE LOGEMENT D'UN SYSTÈME D'ENTRAÎNEMENT
2017-12-13
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2016
|Europäisches Patentamt | 2019
|Aircraft with a fuselage accommodating an unducted turbine engine
Europäisches Patentamt | 2024
|AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
Europäisches Patentamt | 2023
|AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
Europäisches Patentamt | 2023
|